TCDS E7NE

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. E7NE Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E7NE) and other approved data on file with the Federal Aviation Administration meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations, provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. TYPE CERTIFICATE (TC) HOLDER: Intermountain Turbine Services, Inc. 270 South 1060 West Lindon UT, 84042 Type Certificate Holder Record: Honeywell International, Inc. transferred TC E7NE to Intermountain Turbine Services, Inc. on June 9, 2023. TYPE LTP101-600 Axial-centrifugal flow free turbine turboprop. Single stage axial and single stage centri-fugal compressor. Reverse flow annular combustor. Single stage gas generator turbine. Single stage power turbine. LTP101-600A Identical to LTP101-600 except for customer accessory drive and configuration. Reference Installation Drawing No. 4-003-001-01, Sheet 9 of 11. LTP101-600A-1A Identical to -600A, except for improved gas producer turbine wheel. LTP101-700A-1A Similar to -600A-1A, except for higher mass flow compressor. * PAGE 1 2 3 4 5 6 7 REV. 9 8 9 9 8 8 9 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES "DOES NOT APPLY" NOTICE: ALL PAGES ARE REFORMATED. SIGNIFICANT CHANGES, IF ANY, ARE BLACK LINED IN THE LEFT BORDER. E7NE Revision 9 Intermountain Turbine Services, Inc. LTP101-600 LTP101-600A LTP101-600A-1A LTP101-700A-1A June 9, 2023 I. MODELS: LTP101- 600 LTP101- 600A LTP101- 600A-1A LTP101- 700A-1A Output shaft to power turbine speed ratio .052 - - - - - - RATINGS (See NOTE 1) Maximum continuous SHP 565 - - - - 637 ESHP (See NOTE 2) 585 - - - - 665 Output shaft speed, RPM 1924 - - - - - - Measured gas temperature, oF 1365 - - 1380 - - Takeoff (5 minutes) SHP 599 - - - - 671 ESHP (See NOTE 2) 620 - - - - 700 I. MODELS: LTP101-600 LTP101- 600A LTP101- 600A-1A LTP101- 700A-1A Output shaft speed, RPM Measured gas temperature, oF 1924 1405 - - - - 1,440 - - 1,440 - - Output shaft Flanged 4.250' bolt circle, 8 holes, .594" diameter (see applicable Installation Manual Fig. 6.6) - - - - - - Control System Gas Producer Fuel Control Bendix DP- U1 - - - - - - Flow Fence Actuator Bendix AV- P1 - - - - - - Propeller Governor Woodward Constant Speed Propeller Governor P/N 8210 - - - - - - Fuel (See NOTE 3) ASTM D1655-70, Jet A, Jet A1 & Jet B Mil- T- 5624 Grades JP-4 and JP-5 or equivalent - - - - - - Oil (See NOTE 4) Mil-L-7808 Mil- L-23699 - - - - - - Weight (Dry lb. maximum) (Includes essential engine accessories, but excludes starter- generator) 325 - - - - 330 Principal Dimensions Length, in. Nominal Height, in. Nominal Width, in. Nominal 36.8 22.8 23.3 - - - - - - - - - - - - - - - - - - C.G. Location (dry weight) aft of centerline of lower mount pads, in. 1.77 - - - - - - below propeller centerline, in. 3.073 - - - - - - right of propeller centerline, looking aft, in. 0.12 - - - - - - Ignition System (28 Volts D.C.) Ignition exciter unit, Bendix Corporation P/N 10-371440-1, Simmonds Precision P/N 42416, with separate spark plug leads to two shunted surface gap ignitor plugs. - - - - - - Ignitor Plugs AC spark plug P/N 5611304 or Unison, Ind. P/N 10-360840-1 or Champion P/N FHE211-2, CH34016, and CH34016-1 or S.G.L. P/N 0270310 - - - - - - CERTIFICATION BASIS 14 CFR part 33 effective February 1, 1965, including Amendments 33-1, 33-2, 33-3, 33-4, 33-5. MODEL APPLICATION DATE TYPE CERTIFICATE ISSUED / AMENDED LTP101-600 SEPT 18, 1974 JUL 16, 1976 LTP101-600A JUN 16, 1976 JUL 16, 1976 LTP101-600A-1 JUL 21, 1977 NOV 30, 1977 LTP101-600A-1A JUL 21, 1977 NOV 30, 1977 LTP101-600A-1B NOV 3, 1977 NOV 30, 1977 LTP101-600A-1 CANCELED MAY 18, 1979 LTP101-600A-1B CANCELED MAY 18, 1979 LTP101-700A-1A NOV 14, 1977 JUL 11, 1980 PRODUCTION BASIS NONE NOTE 1. Engine ratings are based on calibrated stand performance under the following conditions: Static sea level standard conditions at 59oF and 29.92 in Hg. No airbleed, no duct losses and no external power extraction. Exhaust configuration as specified in Figure 7 of the engine installation instructions, and having an area of 76 square inches. NOTE 2. Equivalent shaft horsepower (ESHP) is based on: ESHP - Jet Thrust, lb + SHP 2.5 NOTE 3. Engines will operate satisfactorily with fuel contaminated to the levels specified in Paragraph 4.4.3 of the engine installation instructions, provided the fuel is introduced to the engine through a filter satisfying the requirements of the subject paragraph. NOTE 4. Mixing of these oils is prohibited. NOTE 5. Maximum permissible gas generator operating speeds (RPM) are as follows: NOTES LTP101-600 LTP101- 600A LTP101- 600A- 1A LTP101- 700A-1A Transient 49,545 - - 50,165 - - Takeoff 49,020 - - 49,399 48,968 Maximum Continuous 48,349 - - 48,681 48,346 NOTE 6. Maximum permissible output shaft torque limits (ft.-lb.) LTP101-600 LTP101- 600A LTP101- 600A-1A LTP101- 700A-1A Transient 1,687 - - - - 1,887 Takeoff 1,634 - - - - 1,832 Maximum Continuous 1,542 - - - - 1,739 NOTE 7. Maximum permissible output shaft speeds (RPM): LTP101-600 LTP101- 600A LTP101- 600A-1A LTP101- 700A-1A Transient 2,112 - - - - 2,032 Takeoff 1,950 - - - - - - Maximum Continuous 1,950 - - - - 1,950 NOTE 8. Maximum permissible temperatures: Measured exhaust gas temperature (oF) measured by eight thermocouples mounted in the combustor housing: LTP101-600 LTP101- 600A LTP101- 600A-1A LTP101- 700A-1A *Starting 1,650 - - - - - - *Transient 1,550 - - - - - - Takeoff 1,405 - - 1,440 - - Maximum Continuous 1,365 - - 1,405 - - *Time limit 12 seconds above 1470oF Component surface (oF), all models: Gas generator speed control Ignition Exciter box Inlet flow modulator Thermocouple harness Electrical harness Oil temperature (oF), all models: (as measured by engine oil temperature bulb) 250 250 350 350 392 210 NOTE 9. Fuel and Oil Pressure Limits (all models): Fuel: 45 p.s.i.a. maximum 15 p.s.i.a. minimum* *The engine is capable of operation to 14,000 feet pressure altitude under the following conditions: (a) Minimum fuel pressure: 4 p.s.i. below atmospheric to 8,000 feet. 3 p.s.i. below atmospheric from 8,000 feet to 14,000 feet. (b) Maximum fuel temperature of 130oF (55oC) at sea level and decreasing linearly to 100oF (43oC) at 14,000 feet. (c) A priming system may be required for engine starting. Oil: Flight Idle and below: 20 p.s.i.g., minimum Maximum Continuous: 100+5 p.s.i.g. NOTE 10 Accessory Drive Provisions (all models): Starter/Generator Overspeed Governor Propeller Governor Customer Accessory Gear Ratio .2512(1) .1157(2) .1157(2) .1157(2) (1) Speed - Times Gas Generator RPM (100% NG = 47,870 RPM). (2) Speed - Times Power Turbine RPM (100% Np = 37,000 RPM or 1,924 RPM output). Starter/Generator Overspeed Governor Propeller Governor Customer Accessory Continuous Torque (in. - lb.) 100 4.0 20 225 Peak Torque During Starts (in.-lb.) 500 - - - Rotation Facing Engine Pad CW CCW CW CCW NOTE 11. These engines meet FAA requirements for operation in icing conditions when the induction system conforms with the applicable Installation Instructions. NOTE 12. These engines have not been tested to evaluate the effects of bird and ice ball ingestion. The bird and ice ball ingestion characteristics of the airframe air inlet and engine combination are to be evaluated prior to the approval of the engine installation. NOTE 13. Maximum permissible air bleed extraction is 5% of inlet airflow at the designated customer bleed port at standard sea level static conditions. NOTE 14. Engine starting torque and speed requirements are as shown in Figure 8 of the applicable Installation Instructions. NOTE 15. These engines may use approved type fuels separately or mixed in any proportion. Fuel control adjustments are not required when switching fuel types. Phillips PFA-55MB anti-icing additive at a concentration not in excess of 0.15% by volume is approved for use in fuels for these engines. NOTE 16. Fuel venting emission control is not included on these engines and therefore airframe compliance must be provided in accordance with SFAR-27. NOTE 17. Certain engine parts are life limited. The limits are listed in FAA approved Service Bulletin No. LT101-71-00-0001 and LT101-71-00-0002. NOTE 18. Engine maintenance program requirements are defined in FAA approved Service Bulletin No. LT101-71- 00-0001. NOTE 19. Deleted (Revision 8) ….END….